Impingement cooled airfoil with bonding foil insert

Claim 2

An airfoil for a gas turbine engine, said airfoil having a leading edge and a trailing edge and comprising: at least 2 diffusion bonded half-section elements having opposed internal walls; and an insert member diffusion bonded between said elements and disposed adjacent to said internal walls, said insert member defining a plurality of radially extending passageways for conducting cooling fluid therethrough and having a plurality of perforations formed therein so as to form an impingement baffle along each of said internal walls for directing said cooling fluid at said internal walls, wherein each of said half section elements comprises rib means projecting inwardly from said internal walls and wherein said insert member is diffusion bonded to said rib means, wherein said insert member comprises channel-shaped sections which fit around said rib means, and wherein said channel-shaped sections are formed with bend portions which provide a clearance between said channel-shaped sections and said rib means.

Claim 3

An airfoil for a gas turbine engine, said airfoil having a leading edge and a trailing edge and comprising: at least two diffusion bonded half-section castings having opposed internal walls interconnected by a diffusion bond extending radially coextensive with said leading edge and said trailing edge; and an insert member diffusion bonded between said castings so as to form said diffusion bond and disposed adjacent to said internal walls, said insert member defining a plurality of radially extending passageways for conducting cooling fluid therethrough and having a plurality of perforations formed therein so as to form an impingement baffle along each of said internal walls for directing said cooling fluid at said internal walls, wherein each of said half section castings comprises rib means projecting inwardly from said internal walls and wherein said insert member is diffusion bonded to said rib means, wherein said insert member comprises channel-shaped sections which fit around said rib means, and wherein said channel-shaped sections are formed with bend portions which provide a clearance between said channel-shaped sections and said rib means.

Claim 4

An airfoil for a gas turbine engine, said airfoil having a leading edge and a trailing edge and comprising: at least two diffusion bonded half-section castings having opposed internal walls interconnected by a diffusion bond extending radially coextensive with said leading edge and said trailing edge; and an insert member diffusion bonded between said castings so as to form said diffusion bond and disposed adjacent to said internal walls, said insert member defining a plurality of radially extending passageways for conducting cooling fluid therethrough and having a plurality of perforations formed therein so as to form an impingement baffle along each of said internal walls for directing said cooling fluid at said internal walls, wherein each of said half section castings comprises rib means projecting inwardly from said internal walls and wherein said insert member is diffusion bonded to said rib means, wherein said insert member comprises channel-shaped sections which fit around said rib means, and wherein said channel-shaped sections are formed with bend portions which provide a clearance between said channel-shaped sections and said rib means.